EP2075506B1 - Habillage de chambre de combustion - Google Patents

Habillage de chambre de combustion Download PDF

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Publication number
EP2075506B1
EP2075506B1 EP08021918.1A EP08021918A EP2075506B1 EP 2075506 B1 EP2075506 B1 EP 2075506B1 EP 08021918 A EP08021918 A EP 08021918A EP 2075506 B1 EP2075506 B1 EP 2075506B1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
ceramic
metallic
air
hollow
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Fee Related
Application number
EP08021918.1A
Other languages
German (de)
English (en)
Other versions
EP2075506A2 (fr
EP2075506A3 (fr
Inventor
Miklos Dr. Gerendas
Sermed Sadig
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP2075506A2 publication Critical patent/EP2075506A2/fr
Publication of EP2075506A3 publication Critical patent/EP2075506A3/fr
Application granted granted Critical
Publication of EP2075506B1 publication Critical patent/EP2075506B1/fr
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/002—Wall structures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/007—Continuous combustion chambers using liquid or gaseous fuel constructed mainly of ceramic components
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/06—Arrangement of apertures along the flame tube
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03041—Effusion cooled combustion chamber walls or domes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03042—Film cooled combustion chamber walls or domes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03044—Impingement cooled combustion chamber walls or subassemblies

Definitions

  • the invention relates to a combustion chamber for a gas turbine according to the features of the preamble of claim 1.
  • the invention relates to a combustion chamber for a gas turbine with a metallic support structure and with a plurality of distributed circumferentially arranged ceramic hollow profiles, which are fixed to the support structure.
  • This prior art is from the DE 195 02 730 A1 previously known.
  • the DE 195 02 730 A1 describes the ceramic lining of a combustion chamber with at least one uncooled wall plate, which consists of high-temperature-resistant structural ceramic and which is connected by means of a fastening element resiliently to a holding device.
  • the bonding surface between the fastener and the ceramic is shaped to provide minimal thermal stress.
  • the disadvantage is that only a convective cooling of the metallic wall is possible, which requires a high cooling air mass flow.
  • the fastener rests on the side facing the hot gas side and is thus exposed to elevated thermal loads.
  • the EP 0 943 867 B1 describes the ceramic lining of a combustion chamber with individual juxtaposed segments in the form of hollow chambers, which can also serve for flow guidance.
  • the ceramic lining can be fixed on the side facing the metallic structure.
  • the cavity can also be provided for cooling guidance and thus achieves higher Heat transfer rates; but this cooling technology is limited only to a convective cooling of the ceramic wall element directed towards the internal combustion chamber. Furthermore, it is not apparent how a dosage of the cooling air takes place and also a control of the local cooling mass flows in the continuous cavity is considered difficult. Another disadvantage is that the entire axial length is made in one piece. The result is that kinks must be mitgefertigt in one piece.
  • the EP 1 431 661 A1 which forms the closest prior art, discloses a plurality of metallic tubular hollow profiles arranged on a support structure on the circumference of a combustion chamber, which are rectilinear and designed as individual segments.
  • a metallic hollow body which is flowed through by cooling air arranged. The resulting heat transfer of the metallic materials results in optimum cooling under all operating conditions.
  • the EP 1 271 056 A1 shows a gas turbine combustor with hollow elements of metallic or ceramic materials.
  • the invention has for its object to provide a combustion chamber of the type mentioned for a gas turbine, which With a simple structure and simple, reliable application is inexpensive to produce and avoids the disadvantages of the prior art.
  • the ceramic, tubular hollow profiles are each formed in a straight line and are arranged as individual segments.
  • a metallic hollow body is arranged, which is preferably formed in the form of a hollow box.
  • On at least one wall air passage openings are provided on the metallic hollow body, which may be formed in the form of a perforation. Through this air passage openings escapes cooling air, which is introduced into the metallic hollow body.
  • the metallic hollow body is preferably arranged to form a gap in the ceramic hollow profile, so that the cooling air flowing through the air passage openings can be distributed in the ceramic hollow profile.
  • the ceramic hollow profile is provided on its wall facing a combustion chamber with additional air passage openings.
  • the air passage openings (perforation) of the metallic hollow body are preferably formed on the combustion chamber interior facing wall to ensure effective cooling of the ceramic hollow profile.
  • the metallic hollow body is preferably connected by means of a cooling air supply line to a cooling air system. Thus, cooling air leaks are avoided.
  • the ceramic hollow profile is formed as a straight profile and when several such ceramic hollow sections are arranged segment-like on the wall of the combustion chamber to form the curved contour of the combustion chamber is particularly favorable.
  • a metallic support structure 6 with segmented in the circumferential and axial direction ceramic tubular hollow sections 2, which can be produced from a section of a straight profile.
  • a one-sided perforated, air-flow, metallic hollow box 1 which is fastened by means of one or more fasteners 7 together with the ceramic hollow section 2 on the metallic support 6.
  • cooling air supply line 8 in the metallic support 6, the ceramic hollow sections 2 and the metallic hollow box 1 is provided, which is as close as possible to a fastener on this and several as centrally located between them.
  • the hollow box through which the cooling air flows serves to control the cooling air.
  • the air passage openings (perforation) 5 which indicates the flow-determining surface, a suitable amount of cooling air in the corresponding area provided for the ceramic hollow profile 2 can be adjusted. Because the metallic hollow box is completed and has only a cooling air supply line 8 and the air passage openings 5, no leakage currents occur.
  • the cooling air that emerges from the metallic hollow box bounces on the back of the ceramic lining 3 and thus significantly increases the heat transfer.
  • the air escapes thereafter at the ends of the ceramic hollow profile and, due to the axial segmentation, can serve for film cooling of the ceramic surface facing the hot gas, but also for protecting the metallic structure from hot gas penetration into the intermediate gaps.
  • a perforation of the hot gas side ceramic surface 9 is advantageous.
  • the one-sided perforated, air-flow, metallic hollow box allows a controlled cooling air distribution in the combustion chamber wall. There are no parasitic leakage currents. Through the perforation of the hollow box, the back of the ceramic surface facing the combustion chamber can be cooled tightly. As a result, the heat flow from the wall is significantly increased. By an additional perforation of the ceramic surface, the cooling effect can be increased again. If the holes for cooling air supply positioned as close as possible to the fasteners, no leakage currents can occur along the gaps between the individual components.
  • the segmented structure makes it possible to produce universally applicable ceramic components that can be used in combustion chambers of any size and shape.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (8)

  1. Chambre de combustion pour une turbine à gaz, comprenant une structure portante (6) métallique ainsi que plusieurs profilés creux (2) tubulaires répartis sur le pourtour et fixés à la structure portante (6), sachant que chaque profilé creux (2) a une forme rectiligne et est disposé en tant que segment individuel, et que dans chaque profilé creux (2) est placé au moins un corps creux (1) métallique qui est muni, sur au moins une paroi, d'orifices de passage d'air (5) à travers lesquels de l'air de refroidissement peut être acheminé, caractérisée en ce que les profilés creux (2) tubulaires sont constitués d'un matériau céramique et qu'une paroi (9) du profilé creux (2) en céramique orientée vers un espace intérieur de la chambre de combustion (12) est munie d'orifices de passage d'air (11).
  2. Chambre de combustion selon la revendication n° 1, caractérisée en ce que le corps creux (1) métallique est disposé dans le profilé creux (2) en céramique en ménageant un espace intermédiaire (13).
  3. Chambre de combustion selon une des revendications n° 1 ou n° 2, caractérisée en ce qu'une paroi du corps creux (1) métallique orientée vers un espace intérieur de la chambre de combustion (12) est munie d'orifices de passage d'air (5).
  4. Chambre de combustion selon une des revendications n° 1 à n° 3, caractérisée en ce que les orifices de passage d'air (5) sont conçus sous la forme d'une perforation.
  5. Chambre de combustion selon une des revendications n° 1 à n° 3, caractérisée en ce que les profilés creux (2) tubulaires en céramique et les corps creux (1) métalliques sont logés sur la structure portante (6) au moyen d'éléments de fixation (7).
  6. Chambre de combustion selon une des revendications n° 1 à n° 5, caractérisée en ce que le corps creux (1) métallique est relié à au moins une conduite d'amenée d'air de refroidissement (8).
  7. Chambre de combustion selon une des revendications n° 1 à n° 6, caractérisée en ce que le profilé creux (2) tubulaire en céramique est conçu sous la forme d'un profilé rectiligne.
  8. Chambre de combustion selon la revendication n° 6, caractérisée en ce que le corps creux (1) métallique est conçu en tant que construction fermée dans laquelle de l'air de refroidissement est introduit uniquement par la conduite d'amenée d'air de refroidissement (8) et évacué uniquement par les orifices de passage d'air (5).
EP08021918.1A 2007-12-27 2008-12-17 Habillage de chambre de combustion Expired - Fee Related EP2075506B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102007062699A DE102007062699A1 (de) 2007-12-27 2007-12-27 Brennkammerauskleidung

Publications (3)

Publication Number Publication Date
EP2075506A2 EP2075506A2 (fr) 2009-07-01
EP2075506A3 EP2075506A3 (fr) 2014-11-12
EP2075506B1 true EP2075506B1 (fr) 2016-04-27

Family

ID=40482017

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08021918.1A Expired - Fee Related EP2075506B1 (fr) 2007-12-27 2008-12-17 Habillage de chambre de combustion

Country Status (3)

Country Link
US (1) US8074453B2 (fr)
EP (1) EP2075506B1 (fr)
DE (1) DE102007062699A1 (fr)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102012213637A1 (de) * 2012-08-02 2014-02-06 Siemens Aktiengesellschaft Brennkammerkühlung
US9651258B2 (en) 2013-03-15 2017-05-16 Rolls-Royce Corporation Shell and tiled liner arrangement for a combustor
EP3022424B1 (fr) * 2013-07-16 2019-10-09 United Technologies Corporation Ensemble de panneau en céramique de moteur de turbine à gaz et procédé de fabrication d'un ensemble de panneau en céramique de moteur de turbine à gaz
WO2015057609A1 (fr) * 2013-10-17 2015-04-23 Harnischfeger Technologies, Inc. Système de blindage pour une benne creusante

Family Cites Families (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3956886A (en) * 1973-12-07 1976-05-18 Joseph Lucas (Industries) Limited Flame tubes for gas turbine engines
US4269032A (en) * 1979-06-13 1981-05-26 General Motors Corporation Waffle pattern porous material
US4512699A (en) 1983-05-17 1985-04-23 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Daze fasteners
US4838031A (en) * 1987-08-06 1989-06-13 Avco Corporation Internally cooled combustion chamber liner
WO1989012789A1 (fr) * 1988-06-13 1989-12-28 Siemens Aktiengesellschaft Bouclier thermique n'exigeant que peu de fluide de refroidissement
DE19502730A1 (de) 1995-01-28 1996-08-01 Abb Management Ag Keramische Auskleidung
DE19730751A1 (de) * 1996-07-24 1998-01-29 Siemens Ag Keramisches Bauteil für eine Wärmeschutzschicht sowie Wärmeschutzschicht
DE59706065D1 (de) * 1996-09-26 2002-02-21 Siemens Ag Hitzeschildkomponente mit kühlfluidrückführung und hitzeschildanordnung für eine heissgasführende komponente
DE19727407A1 (de) * 1997-06-27 1999-01-07 Siemens Ag Hitzeschild
DE29714742U1 (de) * 1997-08-18 1998-12-17 Siemens AG, 80333 München Hitzeschildkomponente mit Kühlfluidrückführung und Hitzeschildanordnung für eine heißgasführende Komponente
DE59806717D1 (de) 1998-03-17 2003-01-30 Alstom Switzerland Ltd Keramische Auskleidung einer Brennkammer
FR2777634B1 (fr) * 1998-04-16 2000-05-19 Snecma Separateur pour chambre de combustion a deux tetes
DE10003728A1 (de) * 2000-01-28 2001-08-09 Siemens Ag Hitzeschildanordnung für eine Heißgas führende Komponente, insbesondere für Strukturteile von Gasturbinen
US6514046B1 (en) * 2000-09-29 2003-02-04 Siemens Westinghouse Power Corporation Ceramic composite vane with metallic substructure
EP1271056A1 (fr) * 2001-06-20 2003-01-02 Siemens Aktiengesellschaft Chambre de combustion de turbine à gaz et méthode pour y amener de l'air
EP1284390A1 (fr) * 2001-06-27 2003-02-19 Siemens Aktiengesellschaft Ensemble bouclier thermique pour un composant acheminant un gaz chaud, notamment pour des pièces de structure de turbines à gaz
EP1431661A1 (fr) * 2002-12-19 2004-06-23 Siemens Aktiengesellschaft Corps de guidage d'écoulement
US7908867B2 (en) * 2007-09-14 2011-03-22 Siemens Energy, Inc. Wavy CMC wall hybrid ceramic apparatus

Also Published As

Publication number Publication date
US20090193810A1 (en) 2009-08-06
EP2075506A2 (fr) 2009-07-01
DE102007062699A1 (de) 2009-07-02
EP2075506A3 (fr) 2014-11-12
US8074453B2 (en) 2011-12-13

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